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1. 发明授权

US08537034B2 Obstacle detection and notification system 有权
标题翻译：障碍物检测和通知系统
公开(公告)号：US08537034B2
公开(公告)日：2013-09-17
申请号：US13296029
申请日：2011-11-14
申请人： Randall A. Greene , Paul Levine , Louis Simons , Robert D. Teter
发明人： Randall A. Greene , Paul Levine , Louis Simons , Robert D. Teter
IPC分类号： G08B21/00
CPC分类号： G08G5/0021 , G08G5/0086 , G08G5/045
摘要： A power line warning system for a helicopter, comprising a positioning system operable to determine the coordinates of the helicopter, an obstacle coordinate database comprising the coordinates of at least a portion of a first power line, a sensor operable to detect electromagnetic radiation from the first power line, and a visual display operable to represent a position of the first power line relative to the helicopter is described. When the coordinates of the first power line are within a predetermined distance of the coordinates of the helicopter, wherein the representation of the position of the first power line is modified when the sensor detects electromagnetic radiation from the first power line.
摘要翻译：一种用于直升机的电力线警报系统，包括可操作以确定直升机的坐标的定位系统，包括第一电力线的至少一部分的坐标的障碍物坐标数据库，可操作以检测来自第一电力线的电磁辐射的传感器描述了可操作以表示第一电力线相对于直升机的位置的视觉显示器。当第一电力线的坐标在直升机的坐标的预定距离内时，其中当传感器检测到来自第一电力线的电磁辐射时，修改第一电力线的位置的表示。

2. 发明授权

US07259685B2 Landing light fault annunciator 有权
标题翻译：着陆灯故障报警器
公开(公告)号：US07259685B2
公开(公告)日：2007-08-21
申请号：US11049957
申请日：2005-02-04
申请人： Randall A. Greene , Paul Levine
发明人： Randall A. Greene , Paul Levine
IPC分类号： G08B21/00
CPC分类号： B60Q11/00 , B64D47/04 , H05B37/03
摘要： A helicopter of the type having an electrical system, a landing light, a master switch and a power supply of between about 18-32 V for operating the electrical system when the master switch is in an on position also includes a landing light fault detector. The landing light fault detector includes a light switch for turning the landing lights on and off and circuit means for detecting a fault in the landing light and for providing a signal indicative of a fault whether or not the light switch is in an on or off position.
摘要翻译：具有电气系统，着陆灯，主开关和用于在主开关处于接通位置时用于操作电气系统的大约18-32V之间的电源的类型的直升机还包括着陆光故障检测器。着陆灯故障检测器包括用于使着陆灯开启和关闭的灯开关和用于检测着陆灯中的故障的电路装置，以及用于提供指示故障的信号，无论灯开关是否处于开或关位置。

3. 发明授权

US07262712B2 Helicopter tactile exceedance warning system 有权
标题翻译：直升机触觉超警预警系统
公开(公告)号：US07262712B2
公开(公告)日：2007-08-28
申请号：US10821974
申请日：2004-04-12
申请人： Randall A. Greene
发明人： Randall A. Greene
IPC分类号： G08B23/00
CPC分类号： F02C9/285 , B64C13/10 , B64C27/04 , B64D43/00 , F05D2270/303 , F05D2270/3032 , F05D2270/44
摘要： A helicopter tactile accedence warning system includes a control stick and a tactile warning device attached to the control stick. A computer or micro processor and a keyboard for entering a safe temperature profile are also provided as well as a thermocouple for measuring the turbine output temperature. The computer compares the actual temperature versus the safe temperature profile and generates a signal to activate the tactile warning device when the actual temperature falls outside of the safe temperature profile to warn a pilot to abort the start. The tactile warning device is also activated during flight operations when an over stress condition occurs to thereby warn the pilot to take corrective action. In addition, the tactile warning may be activated at a first frequency as an early warning and then at a second frequency as an indication of imminent danger.
摘要翻译：直升机触觉入门警告系统包括控制杆和附接到控制棒的触觉警告装置。还提供用于输入安全温度曲线的计算机或微处理器和键盘以及用于测量涡轮机输出温度的热电偶。计算机将实际温度与安全温度曲线进行比较，并在实际温度超出安全温度曲线的情况下产生信号以激活触觉报警装置，以警告飞行员中止启动。触发警告装置在飞行操作期间也会发生过应力状况，从而警告飞行员采取纠正措施。此外，触觉警告可以以第一频率作为早期警告激活，然后以第二频率激活，作为即将发生危险的指示。

4. 发明授权

US06819266B2 System and method for reducing the speed of an aircraft 失效
标题翻译：降低飞机速度的系统和方法
公开(公告)号：US06819266B2
公开(公告)日：2004-11-16
申请号：US10265385
申请日：2002-10-07
申请人： Randall A. Greene
发明人： Randall A. Greene
IPC分类号： G08B2300
CPC分类号： B64D31/06 , G05D1/063
摘要： An aircraft system for reducing the airspeed of an aircraft as it passes through a preselected altitude includes an automatic throttle system including a computer, a device for inputting a preselected altitude and a preselected airspeed into the computer. An altimeter provides the current altitude of the aircraft and an aircraft instrument provides the current air speed and the vertical speed of the aircraft. The computer in response to the current altitude and vertical speed of the aircraft generates a signal to retard the throttles when the current altitude, the current air speed of the aircraft is equal to 2 times the vertical speed plus a preselected altitude.
摘要翻译：一种用于在飞行器经过预选高度时降低空速的飞行器系统包括自动节气门系统，包括计算机，用于输入预选高度的装置和预选的空速进入计算机。高度计提供飞机的当前高度，飞机仪表提供飞行器的当前空气速度和垂直速度。计算机响应当前飞行高度和垂直速度产生一个信号，以阻止节流阀当前的高度，飞机的当前空气速度等于垂直速度的2倍加预选的高度。

5. 发明授权

US06002349A Helicopter anti-torque limit warning device 有权
标题翻译：直升机防扭矩限位报警装置
公开(公告)号：US06002349A
公开(公告)日：1999-12-14
申请号：US133964
申请日：1998-08-14
申请人： Leonard M. Greene , Randall A. Greene
发明人： Leonard M. Greene , Randall A. Greene
IPC分类号： B64C13/10 , B64D43/00 , G08B23/00
CPC分类号： B64C13/10 , B64D43/00
摘要： A pilot warning system is disclosed for a helicopter having a main rotor rotatable about a yaw axis, a fuselage connected to the main rotor and having a tail boom with a controllable force mechanism to counter-act the torque exerted on the fuselage by rotation of the main rotor. The pilot warning system acts on foot pedals operatively connected to the controllable force mechanism, with the pedal movement controlling the amount of force exerted by the controllable force mechanism on the tail boom to the control the orientation of the helicopter fuselage about the yaw axis. A position sensing device senses the location of at least one of the foot pedals between its first and second positions, and a warning indicator operatively connected to the position sensing device provides a warning to the pilot when the sensed foot pedal reaches a predetermined distance from one of the first and second positions. The warning indicator provides a tactile warning into the pilot, such as vibration or shaking of the respective foot pedal to provide an unmistakable warning to the pilot that the foot pedal has reached a predetermined position near its maximum travel position. By such a warning system, the pilot is provided with a tactile input indicating that the helicopter yaw control system is approaching its maximum counter-rotating torque and that he/she should take appropriate action.
摘要翻译：公开了一种用于具有可围绕偏转轴旋转的主转子的直升机的飞行员警告系统，连接到主转子的机身，并具有具有可控力机构的尾臂，以通过旋转来抵抗施加在机身上的扭矩主转子驾驶员警告系统作用于可操作地连接到可控力机构的脚踏板，踏板运动控制由可动力机构施加在尾臂上的力的量，以控制直升机机身绕偏转轴线的取向。位置感测装置感测脚踏板中的至少一个在其第一和第二位置之间的位置，并且当感测到的脚踏板距离一个预定距离达到预定距离时，可操作地连接到位置感测装置的警告指示器向飞行员提供警告的第一和第二职位。警告指示器向飞行员提供触觉警告，例如相应的脚踏板的振动或振动，以向飞行员提供一个明确的警告，脚踏板已经到达其最大行驶位置附近的预定位置。通过这样的警告系统，飞行员具有指示直升机偏航控制系统正在接近其最大反向转矩并且他/她应该采取适当动作的触觉输入。

6. 发明授权

US5986582A Helicopter rotor/engine warning system 失效
标题翻译：直升机转子/发动机警告系统
公开(公告)号：US5986582A
公开(公告)日：1999-11-16
申请号：US103521
申请日：1998-06-24
申请人： Leonard M. Greene , Randall A. Greene
发明人： Leonard M. Greene , Randall A. Greene
IPC分类号： G05D1/00 , G08B23/00
CPC分类号： G05D1/0055
摘要： A two-stage alarm for a rotary wing aircraft, such as a helicopter which operates on a collective control arm. A moveable mass or weight is operatively connected to the collective control arm. The moveable weight may be of a reciprocating type or a rotor driven mass which is mounted eccentrically for rotation about an axs which is spaced from the center of gravity of the weight. In the latter case, a D.C. motor spins the weight rapidly about the axis at a first speed to produce a shaking action to the collective control arm as a warning of an approaching danger. The weight is moved more rapidly to produce a much more noticeable action at a second frequency, or at an increased amplitude as a warning of a more imminent or serious condition which requires immediate action.
摘要翻译：旋翼机的两级报警器，例如在集体控制臂上操作的直升机。可移动质量或重量可操作地连接到集体控制臂。可移动重量可以是往复式或转子驱动质量体，其偏心安装以围绕与重物的重心隔开的斧头旋转。在后一种情况下，直流电动机以第一速度快速地绕轴线旋转重力，以向集体控制臂产生振动作用，作为接近危险的警告。体重更快地移动，以第二频率或以更大幅度产生更明显的动作，作为需要立即采取行动的更迫切或严重的状况的警告。

7. 发明授权

US08033506B2 Apparatus and method for refueling aircraft 有权
标题翻译：用于加油飞机的装置和方法
公开(公告)号：US08033506B2
公开(公告)日：2011-10-11
申请号：US11536256
申请日：2006-09-28
申请人： Randall A. Greene
发明人： Randall A. Greene
IPC分类号： B64D39/00
CPC分类号： G05D1/063 , B64D39/00
摘要： A method and apparatus for aiding pilots in aerial refueling comprises a primary auto-throttling system (ATS) disposed in a primary aircraft and a secondary ATS disposed in a secondary aircraft. The primary ATS includes logic which generates and transmits an anticipatory signal to the secondary ATS. Based upon the received anticipatory signal, the secondary ATS automatically controls a throttle of the secondary aircraft so as to maintain an airspeed of the primary aircraft. The anticipatory signals include rate of change information including at least one of rate of change of airspeed of the primary aircraft, rate of change of pitch of the primary aircraft, and rate of change of weight of the primary aircraft.
摘要翻译：用于在空中加油中辅助飞行员的方法和装置包括设置在主飞行器中的主自动调节系统（ATS）和设置在次飞机中的辅助ATS。主要ATS包括产生和传送预期信号到辅助ATS的逻辑。根据接收到的预期信号，辅助ATS自动控制次级飞机的节气门，以保持主飞机的空速。预期信号包括变化率信息，其包括主飞机的空速变化率，主飞机的俯仰变化率和主飞机的重量变化率中的至少一个。

8. 发明申请

US20080099628A1 APPARATUS AND METHOD FOR REFUELING AIRCRAFT 有权
标题翻译：装备和补救飞机的方法
公开(公告)号：US20080099628A1
公开(公告)日：2008-05-01
申请号：US11536256
申请日：2006-09-28
申请人： Randall A. Greene
发明人： Randall A. Greene
IPC分类号： G05D1/00
CPC分类号： G05D1/063 , B64D39/00
摘要： A method and apparatus for aiding pilots in aerial refueling comprises a primary auto-throttling system (ATS) disposed in a primary aircraft and a secondary ATS disposed in a secondary aircraft. The primary ATS includes logic which generates and transmits an anticipatory signal to the secondary ATS. Based upon the received anticipatory signal, the secondary ATS automatically controls a throttle of the secondary aircraft so as to maintain an airspeed of the primary aircraft. The anticipatory signals include rate of change information including at least one of rate of change of airspeed of the primary aircraft, rate of change of pitch of the primary aircraft, and rate of change of weight of the primary aircraft.
摘要翻译：用于在空中加油中辅助飞行员的方法和装置包括设置在主飞行器中的主自动调节系统（ATS）和设置在次飞机中的辅助ATS。主要ATS包括产生和传送预期信号到辅助ATS的逻辑。根据接收到的预期信号，辅助ATS自动控制次级飞机的节气门，以保持主飞机的空速。预期信号包括变化率信息，其包括主飞机的空速变化率，主飞机的俯仰变化率和主飞机的重量变化率中的至少一个。

9. 发明授权

US6002348A Pilot's aid for detecting power lines 有权
标题翻译：飞行员辅助检测电力线
公开(公告)号：US6002348A
公开(公告)日：1999-12-14
申请号：US156384
申请日：1998-09-18
申请人： Leonard M. Greene , Randall A. Greene
发明人： Leonard M. Greene , Randall A. Greene
IPC分类号： B64C27/00 , B64D45/00 , G08B23/00
CPC分类号： B64C27/006
摘要： An airborne power line detector and warning system includes a low frequency radio and antenna for detecting an AC signal of about 50 to 60 hertz. The system also includes a subsystem for producing a unique audio signal such as a series of clicks for warning a pilot that he is flying close to one or more power lines. In addition, the system includes a mute feature for muting the audio signal and replacing it with a visual signal. Finally, the system includes a gain sensor for replacing the audio signal at any time that the helicopter reduces its distance to a power line. An airborne power line detection and warning system which includes a second system or back up system is also disclosed. That system includes a GPS receiver and GIS data base to position a helicopter with respect to a power line grid and sound an alarm when the helicopter approaches a power line.
摘要翻译：机载电力线检测器和警报系统包括用于检测约50至60赫兹的AC信号的低频无线电和天线。该系统还包括用于产生独特音频信号的子系统，例如用于警告飞行员靠近一个或多个电力线的飞行员的一系列点击。另外，该系统还包括一个静音功能，用于静音音频信号并用视觉信号代替。最后，该系统包括增益传感器，用于在任何时候直升机减小其到电力线的距离的位置来替换音频信号。还公开了一种包括第二系统或备用系统的机载电力线检测和警告系统。该系统包括一个GPS接收器和GIS数据库，用于将直升机相对于电力线网格定位，并且当直升机接近电力线时发出报警。

10. 发明授权

US07126496B2 Tactile cueing system and method for aiding a helicopter pilot in making landings 有权
公开(公告)号：US07126496B2
公开(公告)日：2006-10-24
申请号：US10953607
申请日：2004-09-30
申请人： Randall A. Greene
发明人： Randall A. Greene
IPC分类号： G08B21/00
CPC分类号： B64C13/10 , B64C27/006 , B64C27/57
摘要： A tactile warning system for warning a helicopter pilot of a pre-selected altitude during a landing maneuver includes a collective control arm for control of the aircraft and a tactile warning device operatively connected to the collective control arm. The system includes a radio altimeter for sensing the actual altitude, a computer and keyboard for inputting a pre-selected height above the ground into the computer memory. A signal generator generates a signal indicative of the actual altitude as the aircraft approaches the ground. Then, when the actual altitude is equal to or less then the pre-selected altitude the system activates the tactile device. The warning system indicative of reaching a pre-selected height is also combined with a tactile warning system for avoiding “hot starts” and for avoiding other dangerous conditions.

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